Aircraft system providing passenger entertainment and surveillance features, and associated methods

ABSTRACT

An aircraft system includes an entertainment source, and passenger displays for displaying images from the entertainment source. A signal distribution network connects the entertainment source to the passenger displays. The aircraft system further includes cameras spaced throughout the aircraft for aircraft surveillance, and a pilot display for displaying images from the cameras. The signal distribution network also connects the cameras to the pilot display. The cameras may provide images of internal the aircraft, such as in the cabin area, or external the aircraft. The aircraft system further includes a pilot control unit connected to the pilot display for control thereof.

RELATED APPLICATION

[0001] The present application is a continuation-in-part of U.S. patentapplication Ser. No. 09/544,883 filed Apr. 7, 2000, the entire contentsof which is incorporated herein by reference.

FIELD OF THE INVENTION

[0002] The present invention relates to the field of aircraft systems,and more particularly, to an aircraft system providing passengerentertainment and aircraft surveillance.

BACKGROUND OF THE INVENTION

[0003] Commercial aircraft carry millions of passengers each year. Forrelatively long international flights, wide-body aircraft are typicallyused. These aircraft include multiple passenger aisles and haveconsiderably more space than typical so called narrow-body aircraft.Narrow-body aircraft carry fewer passengers shorter distances, andinclude only a single aisle for passenger loading and unloading.Accordingly, the available space for ancillary equipment is somewhatlimited on a narrow-body aircraft.

[0004] Wide-body aircraft may include full audio and video entertainmentsystems for passenger enjoyment during relatively long flights. Typicalwide-body aircraft entertainment systems may include cabin displays, orindividual seatback displays. Movies or other stored video programmingis selectable by the passenger, and payment is typically made via acredit card reader at the seat. For example, U.S. Pat. No. 5,568,484 toMargis discloses a passenger entertainment system with an integratedtelecommunications system. A magnetic stripe credit card reader isprovided at the telephone handset, and processing to approve the creditcard is performed by a cabin telecommunications unit.

[0005] In addition to prerecorded video entertainment, other systemshave been disclosed including a satellite receiver for live televisionbroadcasts, such as disclosed in French Patent No. 2,652,701 and U.S.Pat. No. 5,790,175 to Sklar et al. The Sklar et al. patent alsodiscloses such a system including an antenna and its associated steeringcontrol for receiving both RHCP and LHCP signals from direct broadcastsatellite (DBS) services. The video signals for the various channels arethen routed to a conventional video and audio distribution system on theaircraft which distributes live television programming to thepassengers.

[0006] In addition, U.S. Pat. No. 5,801,751 also to Sklar et al.addresses the problem of an aircraft being outside of the range ofsatellites, by storing the programming for delayed playback, andadditionally discloses two embodiments—a full system for each passengerand a single channel system for the overhead monitors for a group ofpassengers. The patent also discloses steering the antenna so that it islocked onto RF signals transmitted by the satellite. The antennasteering may be based upon the aircraft navigation system or a CPSreceiver along with inertial reference signals.

[0007] A typical aircraft entertainment system for displaying TVbroadcasts may include one or more satellite antennas, headendelectronic equipment at a central location in the aircraft, a cabledistribution network extending throughout the passenger cabin, andelectronic demodulator and distribution modules spaced within the cabinfor different groups of seats. Many systems require signal attenuatorsor amplifiers at predetermined distances along the cable distributionnetwork. In addition, each passenger seat may include an armrest controland seatback display. In other words, such systems may be relativelyheavy and consume valuable space on the aircraft. Space and weight areespecially difficult constraints for a narrow-body aircraft.

[0008] Published European Patent Application No. 557,058, for example,discloses a video and audio distribution system for an aircraft whereinthe analog video signals are modulated upon individual RF carriers in arelatively low frequency range, and digitized audio signals, includingdigitized data, are modulated upon an RF carrier of a higher frequencyto avoid interference with the modulated video RF carriers. All of thevideo and audio signals are carried by coaxial cables to areadistribution boxes. Each area distribution box, in turn, providesindividual outputs to its own group of floor distribution boxes. Eachoutput line from a floor distribution box is connected to a single lineof video seat electronic boxes (VSEB). The VSEB may service up to fiveor more individual seats. At each seat there is a passenger control unitand a seat display unit. Each passenger control unit includes a set ofchannel select buttons and a pair of audio headset jacks. Each displayunit includes a video tuner that receives video signals from the VSEBand controls a video display.

[0009] A typical cable distribution network within an aircraft may besomewhat similar to a conventional coaxial cable TV system. For example,U.S. Patent No. 5,214,505 to Rabowsky et al. discloses an aircraft videodistribution system including amplifiers, taps and splitters positionedat mutually distant stations and with some of the stations beinginterconnected by relatively long lengths of coaxial cable. A variableequalizer is provided at points in the distribution system to accountfor different cable losses at different frequencies. The patent alsodiscloses microprocessor-controlled monitoring and adjustment of variousamplifiers to control tilt, that is, to provide frequency slopecompensation. Several stations communicate with one another by aseparate communication cable or service path independent of the RFcoaxial cable. The patent further discloses maintenance featuresincluding reporting the nature and location of any failure ordegradation of signals to a central location for diagnostic purposes.

[0010] Camera systems providing surveillance are also available forcommercial aircraft. This is a particularly important feature providedto the pilot, which may be used to anticipate or even prevent in-flightdisturbances by a passenger, for example. U.S. Pat. No. 4,816,828 toFeher discloses cameras internal as well as external the aircraft, withthe images from these cameras being provided to the pilot for viewing.The disclosed camera system is a standalone surveillance system. Thatis, the surveillance system does not share any resources with any of theother systems on the aircraft. This type of configuration negativelyaffects the limited space and weight constraints, particularly for anarrow-body aircraft.

[0011] In contrast, European Patent No. 653,887 discloses an aircraftcamera system integrated with an in-flight entertainment system.However, the images provided by the cameras are for passengerentertainment only. The cameras are placed in the cockpit area of theaircraft for providing take-off and landing images as viewed through thecockpit. Unfortunately, this is of little use in terms aircraftsurveillance.

SUMMARY OF THE INVENTION

[0012] In view of the foregoing background, an object of the presentinvention is to provide an aircraft camera surveillance system and anin-flight entertainment system in accordance with space and weightconstraints for an aircraft, particularly a narrow body aircraft.

[0013] This and other objects, advantages and features in accordancewith the present invention are provided by an aircraft system comprisingat least one entertainment source, at least one passenger display fordisplaying images from the at least one entertainment source, and asignal distribution network connecting the at least one entertainmentsource to the at least one passenger display. The aircraft systempreferably further includes at least one camera for aircraftsurveillance, and at least one pilot display for displaying images fromthe at least one camera. The signal distribution network also preferablyconnects the at least one camera to the at least one pilot display.

[0014] The at least one camera may be positioned to provides images ofinside and/or outside the aircraft. In one embodiment, a plurality ofcameras are spaced throughout a cabin area of the aircraft. Thisadvantageously allows the pilot to monitor the activities of thepassengers. Since the signal distribution network is typically routedthroughout the aircraft for connecting the entertainment source with thepassenger displays, connection of the cameras and the pilot display mayalso be provided via the same signal distribution network. Thisadvantageously eliminates hardware redundancy and is well-suited for thespace and weight constraints of the aircraft.

[0015] The aircraft system preferably further includes a respectivepilot control unit connected to each pilot display. The pilot controlunit may include a camera select mode for selecting the images from adesired camera for viewing, and a scan mode for scanning the images fromeach camera.

[0016] In another embodiment, the at least one camera preferablycomprises at least one passenger camera and at least one pilot camera.The passenger cameras are in the cabin area of the aircraft forproviding images to the pilot display. The pilot camera is in a cockpitarea of the aircraft for providing pilot images to the passengerdisplays. In addition to providing surveillance of the passengers viathe cameras in the cabin area, images from the cockpit may be providedto the passengers for information purposes. For example, the pilotcamera advantageously allows the pilot to be viewed while addressing thepassengers prior to takeoff and landing, for example.

[0017] The aircraft system preferably further comprises a recordingdevice for recording the images from the various cameras. Thisadvantageously allows a particular incident to be later reviewed ifnecessary. In addition, a transmitter may be included as part of theaircraft system for transmitting the images to a location external theaircraft for remote viewing. The remote viewing may be while theaircraft is in-flight, or while the aircraft is on the ground.

[0018] Another aspect of the present invention is directed to a methodfor operating an aircraft system comprising at least one entertainmentsource, at least one passenger display, a signal distribution networkconnecting the least one entertainment source to the at least onepassenger display, at least one camera for aircraft surveillance, atleast one pilot display, and the signal distribution network connectingthe at least one camera to the at least one pilot display. The methodpreferably comprises displaying images from the at least oneentertainment source on the at least one passenger display, anddisplaying images from the at least one camera on the at least one pilotdisplay.

BRIEF DESCRIPTION OF THE DRAWINGS

[0019]FIG. 1 is a schematic diagram of the overall components of theaircraft in-flight entertainment system in accordance with the presentinvention.

[0020]FIGS. 2A and 2B are a more detailed schematic block diagram of anembodiment of the in-flight entertainment system in accordance with thepresent invention.

[0021]FIG. 3 is a schematic rear view of a seatgroup of the in-flightentertainment system of the invention.

[0022]FIG. 4 is a flowchart for a first method aspect relating to thein-flight entertainment system of the invention.

[0023]FIG. 5 is a flowchart for a second method aspect relating to thein-flight entertainment system of the invention.

[0024]FIG. 6 is a more detailed schematic block diagram of a firstembodiment of an antenna-related portion of the in-flight entertainmentsystem of the invention.

[0025]FIG. 7 is a side elevational view of the antenna mounted on theaircraft for the in-flight entertainment system of the invention.

[0026]FIG. 8 is a more detailed schematic block diagram of a secondembodiment of an antenna-related portion of the in-flight entertainmentsystem of the invention.

[0027] FIGS. 9-11 are simulated control panel displays for the in-flightentertainment system of the invention.

[0028]FIG. 12 is a schematic diagram of a portion of the in-flightentertainment system of the invention illustrating a soft-fail featureaccording to a first embodiment.

[0029]FIG. 13 is a schematic diagram of a portion of the in flightentertainment system of the invention illustrating a soft-fail featureaccording to a second embodiment.

[0030]FIG. 14 is a schematic diagram of a portion of the in-flightentertainment system of the invention illustrating a moving map featureaccording to a first embodiment.

[0031]FIG. 15 is a schematic diagram of a portion of the in-flightentertainment system of the invention illustrating a moving map featureaccording to a second embodiment.

[0032]FIG. 16 is a flowchart for a method aspect of the in-flightentertainment system relating to payment and initiation of service inaccordance with the invention.

[0033]FIG. 17 is a schematic block diagram of the portion of thein-flight entertainment system relating to initiation and payment inaccordance with the invention.

[0034]FIG. 18 is a block diagram of another embodiment of an aircraftsystem in accordance with the invention.

[0035]FIG. 19 is a schematic diagram of an aircraft illustratingcomponents of the aircraft system illustrated in FIG. 18.

[0036]FIG. 20 is a block diagram of another embodiment of the aircraftsystem illustrated in FIG. 18.

[0037]FIG. 21 is a partial block diagram of another embodiment of anin-flight entertainment system with a terrestrial TV receiver inaccordance with the invention.

[0038]FIG. 22 is a schematic diagram of an aircraft illustrating theadaptive antenna system illustrated in FIG. 21.

[0039]FIG. 23 is a schematic diagram of a portion of the in-flightentertainment system illustrating a weather information feature inaccordance with the invention.

[0040]FIG. 24 is a schematic diagram of a portion of the in-flightentertainment system illustrating another embodiment of the weatherinformation feature in accordance with the invention.

[0041]FIG. 25 is a flowchart for a method aspect of the in-flightentertainment system relating to determination of pricing levels thereofbased upon passenger profiles in accordance with the invention.

[0042]FIG. 26 is a schematic block diagram of components of thein-flight entertainment system relating to determination of pricinglevels thereof based upon passenger profiles in accordance with theinvention.

[0043]FIG. 27 is a flowchart for a method aspect of the in-flightentertainment system relating to selectively matching advertisementsbased upon passenger profiles in accordance with the invention.

[0044]FIG. 28 is a schematic block diagram of components of thein-flight entertainment system relating to selectively matchingadvertisements based upon passenger profiles in accordance with theinvention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0045] The present invention will be described more fully hereinafterwith reference to the accompanying drawings, in which preferredembodiments of the invention are shown. This invention may, however, beembodied in many different forms and should not be construed as limitedto the embodiments set forth herein; rather, these embodiments areprovided so that this disclosure will be thorough and complete, and willfully convey the scope of the invention to those skilled in the art.Like numbers refer to like elements throughout, and prime notation isused to indicate similar elements in alternate embodiments.

[0046] The major components of an in-flight entertainment system 30 inaccordance with the present invention are initially described withreference to FIGS. 1 through 3. The system 30 receives television and/oraudio broadcast signals via one or more geostationary satellites 33. Thegeostationary satellite 33 may be fed programming channels from aterrestrial station 34 as will be appreciated by those skilled in theart.

[0047] The in-flight entertainment system 30 includes an antenna system35 to be mounted on the fuselage 32 of the aircraft 31. In addition, thesystem 30 also includes one or more multi-channel receiver modulators(MRMs) 40, a cable distribution network 41, a plurality of seatelectronic boxes (SEBs) 45 spaced about the aircraft cabin, and videodisplay units (VDUs) 47 for the passengers and which are connected tothe SEBs. In the illustrated embodiment, the system 30 receives,distributes, and decodes the DBS transmissions from the DBS satellite33. In other embodiments, the system 30 may receive video or TV signalsfrom other classes of satellites as will be readily appreciated by thoseskilled in the art.

[0048] The antenna system 35 delivers DBS signals to the MRMs 40 forprocessing. For example, each MRM 40 may include twelve DBS receiversand twelve video/audio RF modulators. The twelve receivers recover thedigitally encoded multiplexed data for twelve television programs aswill be appreciated by those skilled in the art.

[0049] As shown in the more detailed schematic diagram of FIGS. 2A and2B, an audio video modulator (AVM) 50 is connected to the MRMs 40, aswell as a number of other inputs and outputs. The AVM 50 illustrativelyreceives inputs from an external camera 52, as well as one or more othervideo sources 54, such as videotape sources, and receives signal inputsfrom one or more audio sources 56 which may also be prerecorded, forexample. A PA keyline input and PA audio input are provided forpassenger address and video address override. Audio for any receiveralong with an associated keyline are provided as outputs from the MRM sothat the audio may be broadcast over the cabin speaker system, forexample, as will also be appreciated by those skilled in the art. In theillustrated embodiment, a control panel 51 is provided as part of theAVM 50. The control panel 51 not only permits control of the system, butalso displays pertinent system information and permits variousdiagnostic or maintenance activities to be quickly and easily performed.

[0050] The AVM 50 is also illustratively coupled to a ground data linkradio transceiver 57, such as for permitting downloading or uploading ofdata or programming information. The AVM 50 is also illustrativelyinterfaced to an air-to-ground telephone system 58 as will beappreciated by those skilled in the art.

[0051] The AVM 50 illustratively generates a number of NTSC videooutputs which may be fed to one or more retractable monitors 61 spacedthroughout the cabin. Power is preferably provided by the aircraft 400Hz AC power supply as will also be appreciated by those skilled in theart. Of course, in some embodiments, the retractable monitors may not beneeded.

[0052] The MRMs 40 may perform system control, and status monitoring. AnRF distribution assembly (RDA) 62 can be provided to combine signalsfrom a number of MRMs, such as four, for example. The RDA 62 combinesthe MRM RF outputs to create a single RF signal comprising up to 48audio/video channels, for example. The RDA 62 amplifies and distributesthe composite RF signal to a predetermined number of zone cable outputs.Eight zones are typical for a typical narrow-body single-aisle aircraft31. Depending on the aircraft, not all eight outputs may be used. Eachcable will serve a zone of seatgroups 65 in the passenger cabin.

[0053] Referring now more specifically to the lower portion of FIG. 2Band also to FIG. 3, distribution of the RF signals and display of videoto the passengers is now further described. Each zone cable 41 feeds theRF signal to a group of contiguous seatgroups 65 along either the rightor left hand side of the passenger aisle. In the illustrated embodiment,the seatgroup 65 includes three side-by-side seats 66, although thisnumber may also be two for other types of conventional narrow-bodyaircraft.

[0054] The distribution cables 41 are connected to the first SEB 45 ineach respective right or left zone. The other SEBs 45 are daisy-chainedtogether with seat-to-seat cables. The zone feed, and seat-to-seatcables preferably comprise an RF audio video coaxial cable, a 400 cyclepower cable, and RS 485 data wiring.

[0055] For each seat 66 in the group 65, the SEB 45 tunes to anddemodulates one of the RF modulated audio/video channels. The audio andvideo are output to the passenger video display units (VDUs) 68 andheadphones 70, respectively. The tuner channels are under control of thepassenger control unit (PCU) 71, typically mounted in the armrest of theseat 66, and which also carries a volume control.

[0056] Each VDU 68 may be a flat panel color display mounted in theseatback. The VDU 68 may also be mounted in the aircraft bulkhead inother configurations as will be appreciated by those skilled in the art.The VDU 68 will also typically include associated therewith a userpayment card reader 72. The payment card reader 72 may be a credit cardreader, for example, of the type that reads magnetically encodedinformation from a stripe carried by the card as the user swipes thecard through a slot in the reader as will be appreciated by thoseskilled in the art. In some embodiments, the credit card data may beprocessed on the aircraft to make certain processing decisions relatingto validity, such as whether the card is expired, for example. Asdescribed in greater detail below, the payment card reader 72 may alsobe used as the single input required to activate the system for enhanceduser convenience.

[0057] Having now generally described the major components of thein-flight entertainment system 30 and their overall operation, thedescription now is directed to several important features andcapabilities of the system in greater detail. One such feature relatesto flexibility or upgradability of the system as may be highly desirablefor many airline carriers. In particular, the system 30 is relativelycompact and relatively inexpensive so that it can be used on narrow-bodyaircraft 31, that is, single-aisle aircraft. Such narrow-body aircraft31 are in sharp contrast to wide-body aircraft typically used on longeroverseas flights and which can typically carry greater volumes andweight. The narrow-body aircraft 31 are commonly used on shorterdomestic flights

[0058] The system 30, for example, can be first installed to provideonly audio. In addition, the first class passengers may be equipped withseat back VDUs 68, while the coach section includes only aisle mountedvideo screens. The important aspect that permits upgradability is thatthe full cable distribution system is installed initially to therebyhave the capacity to handle the upgrades. In other words, the presentinvention permits upgrading and provides reconfiguration options to theair carrier for an in-flight entertainment system and while reducingdowntime for such changes.

[0059] The cable distribution system is modeled after a conventionalground based cable TV system in terms of signal modulation, cabling,drops, etc. Certain changes are made to allocate the available channels,such as forty-eight, so as not to cause potential interference problemswith other equipment aboard the aircraft 31 as will be appreciated bythose skilled in the art. In addition, there are basically no activecomponents along the cable distribution path that may fail, for example.The cable distribution system also includes zones of seatgroups 66. Thezones provide greater robustness in the event of a failure. The zonescan also be added, such as to provide full service throughout the cabin.

[0060] Referring now additionally to the flow chart of FIG. 4, a methodfor installing and operating an aircraft in-flight entertainment systemin accordance with the invention is now described. After the start(Block 80), the method preferably comprises installing at least oneentertainment source on the aircraft at Block 82. The entertainmentsource may include a satellite TV source, such as provided by the DBSantenna system 35 and MRMs 40 described above. The method at Block 84also preferably includes installing a plurality of spaced apart signaldistribution devices, each generating audio signals for at least onepassenger in an audio-only mode, and generating audio and video signalsto at least one passenger in an audio/video mode. These devices may bethe SEBs 45 described above as will be readily appreciated by thoseskilled in the art. The SEBs 45 include the capability for both audioand video when initially installed to thereby provide the flexibilityfor upgrading.

[0061] At Block 86 the cable network is installed on the aircraft 31connecting the at least one entertainment source to the signaldistribution devices. In other words, the MRMs 40 are connected to theSEBs 45 in the various equipped zones throughout the aircraft 31.Operating the aircraft in-flight entertainment system 30 at Block 88with at least one predetermined signal distribution device in theaudio-only mode, permits initial weight and cost savings since the VDUs68, for example, may not need to be initially installed for allpassengers as will be appreciated by those skilled in the art. Forexample, a carrier may initially decide to equip first class passengerswith both video and audio entertainment options, while coach passengersare initially limited to audio only. Hence, the cost of the VDUs 68 forthe coach passengers is initially deferred.

[0062] Installing the cabling 41 and SEBs 45 at one time will result insubstantial time and labor savings as compared to a piecemeal approachto adding these components at a later time as needed. Accordingly,should an upgrade be desired at Block 90, this may be readilyaccomplished by connecting at least one VDU 68 to the at least onepredetermined signal distribution device, or SEB 45, to operate in theaudio/video mode and while leaving the cable network unchanged (Block92). Accordingly, the downtime experienced by an air carrier is greatlyreduced over other systems which require significant recabling and otherdifficult equipment installation operations for upgrading. The method isparticularly advantageous for a single-aisle narrow-body aircraft 31 asshown in the illustrated embodiment, where cost effectiveness and lowweight are especially important.

[0063] As noted above, the entertainment source may preferably comprisea DBS receiver. The step of later upgrading may further comprise leavingthe at least one predetermined signal distribution device, such as theSEB 45, unchanged. The step of installing the cable network 41 maycomprise installing coaxial cable, power cable and data cable throughoutthe aircraft as also described above. The step of later upgrading mayinclude installing at least one VDU 68 in the aircraft 31, such as onbacks of passenger seats 66.

[0064] Of course, the aircraft 31 in some embodiments may includedifferent seating classes as will be appreciated by those skilled in theart. Accordingly, another important aspect of the invention relates tooffering different entertainment services based upon the differentseating classes at Block 94. In addition, the different seating classesmay be reconfigurable, and the step of reconfiguring offeredentertainment services may then be based upon reconfiguring of theseating classes. The offering of different entertainment services maycomprise offering different packages of television channels, forexample. In addition, the step of offering different entertainmentservices may comprise offering audio-only and audio/video modes ofoperation based upon seating classes.

[0065] Yet another aspect of the invention relates to a method foroperating an aircraft in-flight entertainment system 30 for an aircraft31 when seating classes are reconfigured. Continuing down the flowchartof FIG. 4, this aspect of the method preferably comprises determiningwhether a reconfiguration is desired at Block 96, and reconfiguringoffered entertainment services based upon reconfiguring of the seatingclasses at Block 98 before stopping at Block 100. For example, the stepof offering different entertainment services may include offeringdifferent packages of television channels. Alternately, the step ofoffering different entertainment services may comprise offeringaudio-only and audio/video modes of operation based upon seatingclasses. In either case, the reconfiguring can be readily accomplishedusing the existing cable distribution network 41 and distributiondevices, that is, SEBs 45 as will be appreciated by those skilled in theart.

[0066] The various upgrading and reconfiguring aspects of the in-flightentertainment system 30 can be performed in a reverse sequence than thatillustrated in FIG. 4 and described above. of course, the upgrade stepsmay be practiced without the later reconfiguring steps as will beappreciated by those skilled in the art.

[0067] To further illustrate the method aspects, the flowchart of FIG. 5is directed to the subset of offering different services and laterreconfiguring those services based upon reconfiguring seating. Moreparticularly, from the start (Block 110), the in-flight entertainmentsystem 30 is installed and operated (Block 114) for offering differentservices based upon seating class, such as offering video to first classpassengers, and offering only audio to non-first class passengers. If itis determined that the seating should be reconfigured at Block 116, thenthe in-flight entertainment system 30 can be readily reconfigured atBlock 118 before stopping (Block 120).

[0068] Turning now additionally to FIGS. 6 and 7, advantages andfeatures of the antenna system 35 are now described in greater detail.The antenna system 35 includes an antenna 136 which may be positioned orsteered by one or more antenna positioners 138 as will be appreciated bythose skilled in the art. In addition, one or more position encoders 141may also be associated with the antenna 136 to steer the antenna tothereby track the DBS satellite or satellites 33. Of course, apositioning motor and associated encoder may be provided together withina common housing, as will also be appreciated by those skilled in theart. In accordance with one significant advantage of the presentinvention, the antenna 136 may be steered using received signals in therelatively wide bandwidth of at least one DBS transponder.

[0069] More particularly, the antenna system 35 includes an antennasteering controller 142, which, in turn, comprises the illustrated fulltransponder bandwidth received signal detector 143. This detector 143generates a received signal strength feedback signal based upon signalsreceived from the full bandwidth of a DBS transponder rather than asingle demodulated programming channel, for example. Of course, in otherembodiments the same principles can be employed for other classes ortypes of satellites than the DBS satellites described herein by way ofexample.

[0070] In the illustrated embodiment, the detector 143 is coupled to theoutput of the illustrated intermediate frequency interface (IFI) 146which converts the received signals to one or more intermediatefrequencies for further processing by the MRMs 40 as described above andas will be readily appreciated by those skilled in the art. In otherembodiments, signal processing circuitry, other than that in the IFI 146may also be used to couple the received signal from one or more fullsatellite transponders to the received signal strength detector 143 aswill also be appreciated by those skilled in the art.

[0071] A processor 145 is illustratively connected to the receivedsignal strength detector 143 for controlling the antenna steeringpositioners 138 during aircraft flight and based upon the receivedsignal strength feedback signal. Accordingly, tracking of the satelliteor satellites 33 is enhanced and signal service reliability is alsoenhanced.

[0072] The antenna steering controller 142 may further comprise at leastone inertial rate sensor 148 as shown in the illustrated embodiment,such as for roll, pitch or yaw as will be appreciated by those skilledin the art. The rate sensor 148 may be provided by one or more solidstate gyroscopes, for example. The processor 145 may calibrate the ratesensor 148 based upon the received signal strength feedback signal.

[0073] The illustrated antenna system 35 also includes a globalpositioning system (GPS) antenna 151 to be carried by the aircraftfuselage 32. This may preferably be provided as part of an antennaassembly package to be mounted on the upper portion of the fuselage. Theantenna assembly may also include a suitable radome, not shown, as willbe appreciated by those skilled in the art. The antenna steeringcontroller 142 also illustratively includes a GPS receiver 152 connectedto the processor 145. The processor 145 may further calibrate the ratesensor 148 based upon signals from the GPS receiver as will beappreciated by those skilled in the art.

[0074] As will also be appreciated by those skilled in the art, theprocessor 145 may be a commercially available microprocessor operatingunder stored program control. Alternately, discrete logic and othersignal processing circuits may be used for the processor 145. This isalso the case for the other portions or circuit components described asa processor herein as will be appreciated by those skilled in the art.The advantageous feature of this aspect of the invention is that thefull or substantially full bandwidth of the satellite transponder signalis processed for determining the received signal strength, and thisprovides greater reliability and accuracy for steering the antenna 136.

[0075] Another advantage of the antenna system 35 is that it may operateindependently of the aircraft navigation system 153 which isschematically illustrated in the lower right hand portion of FIG. 6. Inother words, the aircraft 31 may include an aircraft navigation system153, and the antenna steering controller 142 may operate independentlyof this aircraft navigation system. Thus, the antenna steering mayoperate faster and without potential unwanted effects on the aircraftnavigation system 153 as will be appreciated by those skilled in theart. In addition, the antenna system 35 is also particularlyadvantageous for a single-aisle narrow-body aircraft 31 where costeffectiveness and low weight are especially important.

[0076] Turning now additionally to FIG. 8, another embodiment of theantenna system 35′ is now described which-includes yet furtheradvantageous features. This embodiment is directed to functioning inconjunction with the three essentially collocated geostationarysatellites for the DIRECTV® DBS service, although the invention isapplicable in other situations as well. For example, the DIRECTV®satellites may be positioned above the earth at 101 degrees westlongitude and spaced 0.5 degrees from each other. Of course, theseDIRECTV® satellites may also be moved from these example locations, andmore than three satellites may be so collocated. Considered in somewhatbroader terms, these features of the invention are directed to two ormore essentially collocated geostationary satellites. Different circularpolarizations are implemented for reused frequencies as will beappreciated by those skilled in the art.

[0077] In this illustrated embodiment, the antenna 136′ is a multi beamantenna having an antenna boresight (indicated by reference B), and alsodefining right-hand circularly polarized (RHCP) and left-hand circularlypolarized (LHCP) beams (designated RHCP and LHCP in FIG. 8) which areoffset from the antenna boresight. Moreover, the beams RHCP, LHCP areoffset from one another by a beam offset angle α which is greatlyexaggerated in the figure for clarity. This beam offset angle α is lessthan the angle β defined by the spacing defined by the satellites 33 a,33 b. The transponder or satellite spacing angle β is about 0.5 degrees,and the beam offset angle α is preferably less than 0.5 degrees, and maybe about 0.2 degrees, for example.

[0078] The beam offset angle provides a squinting effect which allowsthe antenna 136′ to be made longer and thinner than would otherwise berequired, and the resulting shape is highly desirable for aircraftmounting as will be appreciated by those skilled in the art. Thesquinting also allows the antenna to be constructed to have additionalsignal margin when operating in rain, for example, as will also beappreciated by those skilled in the art.

[0079] The multi-beam antenna 136′ may be readily constructed in aphased array form or in a mechanical form as will be appreciated bythose skilled in the art without requiring further discussion herein.Aspects of similar antennas are disclosed in U.S. Pat. Nos. 4,604,624 toAmitay et al.; 5,617,108 to Silinsky et al.; and 4,413,263 also toAmitay et al.; the entire disclosures of which are incorporated hereinby reference.

[0080] The processor 145′ preferably steers the antenna 136′ based uponreceived signals from at least one of the RHCP and LHCP beams which areprocessed via the IFI 146′ and input into respective received signalstrength detectors 143 a, 143 b of the antenna steering controller 142′.In one embodiment, the processor 145′ steers the multi-beam antenna 136′based on a selected master one of the RHCP and LHCP beams and slaves theother beam therefrom.

[0081] In another embodiment, the processor 145′ steers the multi-beamantenna 136′ based on a predetermined contribution from each of the RHCPand LHCP beams. For example, the contribution may be the same for eachbeam. In other words, the steering or tracking may such as to averagethe received signal strengths from each beam as will be appreciated bythose skilled in the art. As will also be appreciated by those skilledin the art, other fractions or percentages can also be used. Of course,the advantage of receiving signals from two different satellites 33 a,33 b is that more programming channels may then be made available to thepassengers.

[0082] The antenna system 35′ may also advantageously operateindependent of the aircraft navigation system 153′. The other elementsof FIG. 8 are indicated by prime notation and are similar to thosedescribed above with respect to FIG. 6. Accordingly, these similarelements need no further discussion.

[0083] Another aspect of the invention relates to the inclusion ofadaptive polarization techniques which may be used to avoid interferencefrom other satellites. In particular, low earth orbit satellites (LEOS)are planned which may periodically be in position to cause interferencewith the signal reception by the in-flight entertainment system 30.Adaptive polarization techniques would also be desirable should assignedorbital slots for satellites be moved closer together.

[0084] Accordingly, the processor 145′ may preferably be configured toperform adaptive polarization techniques to avoid or reduce the impactof such potential interference. Other adaptive polarization techniquesmay also be used. Suitable adaptive polarization techniques aredisclosed, for example, in U.S. Pat. Nos. 5,027,124 to Fitzsimmons etal; 5,649,318 to Lusignan; and 5,309,167 to Cluniat et al. The entiredisclosures of each of these patents is incorporated herein byreference. Those of skill in the art will readily appreciate theimplementation of such adaptive polarization techniques with thein-flight entertainment system 30 in accordance with the presentinvention without further discussion.

[0085] Other aspects and advantages of the in-flight entertainmentsystem 30 of the present invention are now explained with reference toFIGS. 9-11. The system 30 advantageously incorporates a number ofself-test or maintenance features. As will be appreciated by thoseskilled in the art, the maintenance costs to operate such a system 30could be significantly greater than the original purchase price.Accordingly, the system 30 includes test and diagnostic routines topinpoint defective equipment. In particular, the system 30 provides thegraphical representation of the aircraft seating arrangement to indicateclass of service, equipment locations, and failures of any of thevarious components to aid in maintenance.

[0086] As shown in FIG. 9, the system 30 includes a control paneldisplay 51, and a processor 160 connected to the control panel display.The control panel display 51 and processor 160 may be part of the AVM 50(FIG. 1), but could be part of one or more of the MRMs 40 (FIG. 1), orpart of another monitoring device as will be appreciated by thoseskilled in the art. The control panel display 51 may be touch screentype display including designated touch screen input areas 163 a-163 dto also accept user inputs as would also be appreciated by those skilledin the art.

[0087] More particularly, the processor 160 generates a seating layoutimage 170 of the aircraft on the control panel display 51 with locationsof the signal distribution devices located on the seating layout image.These locations need not be exact, but should be sufficient to directthe service technician to the correct left or right side of thepassenger aisle, and locate the seatgroup and/or seat location for thedefective or failed component. In addition, the locations need not beconstantly displayed; rather, the location of the component may only bedisplayed when service is required, for example.

[0088] The processor 160 also preferably generates information relatingto operation of the signal distribution devices on the display. Thesignal distribution devices, for example, may comprise demodulators(SEBs 45), modulators (MRMs 40), or the video passenger displays (VDUs68), for example. Accordingly, a user or technician can readilydetermine a faulty component and identify its location in the aircraft.

[0089] As shown in the illustrated embodiment of FIG. 9, therepresentative information is a failed power supply module of the #4 SEBof zone 5. In FIG. 10, the information is for a failed #4 MRM. Thisinformation is illustratively displayed in text with an indicatorpointing to the location of the device. In other embodiments, a flashingicon or change of color could be used to indicate the component orsignal distribution device requiring service as will be appreciated bythose skilled in the art.

[0090] This component mapping and service needed feature of theinvention can be extended to other components of the system 30 as willbe readily appreciated by those skilled in the art. For example, theprocessor 160 may further generate information relating to operation ofthe entertainment source, such as the DBS receiver, or its antenna asshown in FIG. 11. Again, the technician may be guided to the location ofthe failed component from the seat image layout 170.

[0091] Returning again briefly to FIG. 9, another aspect of theinvention relates to display of the correct seating layout 170 for thecorresponding aircraft 31. As shown, the display 51 may also include anaircraft-type field 171 which identifies the particular aircraft, suchas an MD-80. The corresponding seating layout data can be downloaded tothe memory 162 or the processor 160 by a suitable downloading device,such as the illustrated laptop computer 161. In other embodiments, theprocessor 160 may be connected to a disk drive or other data downloadingdevice to receive the seat layout data.

[0092] The seat layout data would also typically include the data forthe corresponding locations of the devices installed as part of thein-flight entertainment system 30 on the aircraft as will be appreciatedby those skilled in the art. Accordingly, upgrades or changes in thesystem 30 configuration may thus be readily accommodated.

[0093] Another aspect of the invention relates to a soft failure modeand is explained with reference to FIGS. 12 and 13. A typical DBS systemprovides a default text message along the lines “searching forsatellite” based upon a weak or missing signal from the satellite. Ofcourse, an air traveler may become disconcerted by such a message, sincethis may raise possible questions about the proper operation of theaircraft. In other systems, a weak received signal may cause thedisplayed image to become broken up, which may also be disconcerting tothe air traveler.

[0094] The system 30 as shown in FIG. 12 of the present inventionincludes a processor 175 which may detect the undesired condition in theform of a weak or absent received signal strength, and cause thepassenger video display 68 to display a substitute image. Moreparticularly, the processor 175 may be part of the AVM 50 as describedabove, could be part of another device, such as the MRM 40, or could bea separate device.

[0095] The processor 175 illustratively includes a circuit or portion176 for determining a weak received signal strength as will beappreciated by those skilled in the art. Suitable circuit constructionsfor the weak received signal strength determining portion or circuit 176will be readily appreciated by those skilled in the art, and require nofurther discussion herein. The threshold for the weak received signalstrength determining portion or circuit 176 can preferably be set so asto trigger the substitute image before substantial degradation occurs,or before a text default message would otherwise be triggered, dependingon the satellite service provider, as would be appreciated by thoseskilled in the art. In addition, the substitute image could be triggeredfor a single programming channel upon a weakness or loss of only thatsingle programming channel, or may be generated across the board for allprogramming channels as will be readily appreciated by those skilled inthe art.

[0096] In the illustrated system 30 of FIG. 12, a substitute imagestorage device 178 is coupled to the processor 175. This device 178 maybe a digital storage device or a video tape player, for example, forcausing the passenger video display 68 to show a substitute image. Forexample, the image could be a text message, such as “LiveTV™ ServiceTemporarily Unavailable, Please Stand By”. Of course, other similarmessages or images are also contemplated by the invention, and whichtend to be helpful to the passenger in understanding a loss ofprogramming service has occurred, but without raising unnecessaryconcern for the proper operation of the aircraft 31 to the passenger.

[0097] This concept of a soft failure mode, may also be carried forwardor applied to a component malfunction, for example. As shown in thesystem 30′ of FIG. 13, a component malfunctioning determining portion orcircuit 177′ is added to the processor 175′ and can be used incombination with the weak received signal strength determining portion176′. Of course, in other embodiments the malfunction determiningcircuit portion 177′ could be used by itself. Again, rather than have adisconcerting image appear on the passenger's video display 68, asubstitute image may be provided. Those of skill in the art willappreciate that the weak received signal strength and componentmalfunction are representative of types of undesired conditions that thepresent system 30 may determine and provide a soft failure mode for.

[0098] Yet another advantageous feature of the invention is nowexplained with reference to FIG. 14. Some commercial aircraft provide,on a common cabin display or overhead monitor, a simulated image of theaircraft as it moves across a map between its origin and destination.The image may also include superimposed data, such as aircraft position,speed, heading, altitude, etc. as will be appreciated by those skilledin the art.

[0099] The in-flight entertainment system 30 of the invention determinesor receives the aircraft position during flight and generates a movingmap image 195 of the aircraft as a flight information video channel.Various flight parameters 196 can also be displayed along with themoving map image 195. This flight information channel is offered alongwith the DBS programming channels during aircraft flight. In theillustrated embodiment, the passenger may select the flight informationchannel to be displayed on the passenger video display 68 using thepassenger control unit (PCU) 71 which is typically mounted in thearmrest as described above. In other words, the flight informationchannel is integrated along with the entertainment programming channelsfrom the DBS system.

[0100] As shown in the illustrated embodiment, the moving map image 195including other related text, such as the flight parameters 196, may begenerated by the illustrated AVM 50 and delivered through the signaldistribution network 41 to the SEB 45. Since the antenna steeringcontroller 142 (FIG. 6) includes circuitry for determining the aircraftposition, etc., these devices may be used in some embodiments forgenerating the moving map image as will be appreciated by those skilledin the art.

[0101] For example, the GPS receiver 152 and its antenna 151 can be usedto determine the aircraft position. The GPS receiver 152 is also used tosteer the antenna in this embodiment. In other embodiments a separateGPS receiver may be used as will be appreciated by those skilled in theart. As will also be appreciated by those skilled in the art, theinertial rate sensor(s) 148 of the antenna steering controller 142 mayalso be used in some embodiments for generating flight information.

[0102] The processor 190 illustratively includes a parameter calculator191 for calculating the various displayed flight parameters 196 from theposition signal inputs as will be appreciated by those skilled in theart. For example, the parameter calculator 191 of the processor 190 maydetermine at least one of an aircraft direction, aircraft speed andaircraft altitude for display with the map image. Information may alsobe acquired from other aircraft systems, such as an altimeter 197, forexample, as will be appreciated by those skilled in the art. Also, theillustrated embodiment includes a map image storage device 192 which mayinclude the various geographic maps used for the moving map image 195.

[0103] Weather information may also be added for display along with themoving map image 195. Further details on the generation and display ofmoving map images may be found in U.S. Pat. Nos. 5,884,219 to Curtwrightet al. and 5,992,882 to Simpson et al., the entire disclosures of whichare incorporated herein by reference.

[0104] Referring now briefly additionally to FIG. 15, another embodimentof the system 30 including the capability to display a flightinformation channel among the offered DBS or satellite TV channels isnow described. In this embodiment, a moving map image generator 198′ isadded as a separate device. In other words, in this embodiment, theflight channel signal is only carried through the distribution cablenetwork 41′ and delivered via the SEB 45′ to the passenger video display68, and there is no interface to the components of the antenna steeringcontroller 142 as in the embodiment described with reference to FIG. 14.In this embodiment, the moving map image generator 198′ may include itsown position determining devices, such as a GPS receiver. Alternately,the moving map image generator 198′ may also receive the position dataor even the image signal from a satellite or terrestrial transmitter.

[0105] Referring now additionally to the flowchart of FIG. 16 and theassociated schematic block diagram of FIG. 17, another advantageousaspect of the invention relating to initiation and payment is nowdescribed. In particular, from the start (Block 200), the system 30 maybe first powered up and it performs its test and maintenance checks atBlock 202 as will be appreciated by those skilled in the art. If thesystem components are determined to be operating correctly (Block 204),the payment card readers 72 are monitored at Block 208. If there is afailure, an alarm may be generated (Block 206) so that corrective actionmay be taken.

[0106] The payment card 210 carried and presented by the passenger forpayment may be a credit card, for example, and which includes a plasticsubstrate 211 and a magnetic stripe 212 thereon. The payment card 210may also be a debit card, an automated teller machine (ATM) card, afrequent flyer card, or a complimentary card provided by the airline orthe entertainment service provider for example. Other types of paymentcards are also contemplated by the present invention as will beappreciated by those skilled in the art. The magnetic stripe 212includes identification information thereon, and may also includeexpiration data encoded as will be appreciated by those skilled in theart. In the illustrated embodiment, the card reader 72 is a swipe-typereader, wherein the passenger simply swipes the correctly oriented card210 through a receiving channel or slot.

[0107] Other types of card readers are also contemplated by the presentinvention as will be appreciated by those skilled in the art. Forexample, the system 30 can also be readily compatible with smart cardtechnology. A smart card reader 215 is shown in the right hand portionof FIG. 17. As will be understood by those skilled in the art, the smartcard 216 may include a plastic substrate 217 which carries an integratedcircuit 218. The integrated circuit 218 is read or communicated with toarrange for payment. The connection to the integrated circuit 218 may bethrough contacts 219 carried by the substrate 217, or can be throughshort range wireless coupling as will be appreciated by those skilled inthe art.

[0108] In the illustrated embodiment, the passenger video display 68 isconnected to the SEB 45, which in turn is connected, via the cablenetwork 41, to the upstream DBS receiver as explained in detail above.The SEB 45 is also connected to the PCU 71 to permit user channelselection, volume control, etc. as will be appreciated by those skilledin the art. Passenger headphones 70 are also illustratively connected tothe PCU 71.

[0109] On a typical narrow-body aircraft 31, the flight attendants arebusy serving food and beverages during the relatively short duration ofthe flight. Accordingly, if the system 30 could only be manuallyinitiated by the flight attendant after handling a cash exchange, suchwould be very impractical.

[0110] In accordance with the present invention, passenger and airlineconvenience are greatly enhanced based upon using the passenger'spresentation of his payment card 210 to initiate service. In otherwords, returning again to the flowchart of FIG. 16, if a monitored cardreader 72 is determined to have had a card 210 presented thereto (Block210), the card is read at Block 212.

[0111] The processor 220 of the SEB 45 may perform certain basicvalidity checks on the read data as will be appreciated by those skilledin the art. For example, the processor 220 could provide a check of thevalidity of the expiration date of the payment card 210. Other validitychecks could also be performed, although contact with an authorizationcenter would not typically be desired For example, the payment card typecould also be checked against a preprogrammed list of acceptable orauthorized card types. For example, the identifying data may indicatewhether the card is an American Express, VISA, Delta Airlines, orservice provider complimentary card.

[0112] In addition, a data validity or numerical sequence test, such asa CRC test, could be performed on the data to determine its validity.For example, the data may include data necessary to the financialtransaction, such as the account number, person's name, expiration date,etc. and additional data which causes the data collectively to pass acertain mathematical function test. In other words, if the card 210 wasinvalid as determined at Block 214, service could be denied, and/or acertain number of retries could be permitted.

[0113] At Block 216, if the optional validity check is successful, theselection and display of the programming channels is enabled beforestopping (Block 218). Moreover, in accordance with the invention, theonly needed or required initiation input from the passenger is thepresentation of a valid payment card 210. The passenger need not enterpersonalized passwords or hard to remember codes. Accordingly, passengerconvenience is greatly enhanced. Risk of revenue loss to the airline isalso relatively small since the airline has a record of the assignedpassenger for each seat. In addition, the service fee is relativelysmall.

[0114] Although the payment reader 72 has been described for a paymentcard 210, the invention is also more broadly applicable to any usercarried token which includes identifying date thereon for payment.Accordingly, many modifications and other embodiments of the inventionwill come to the mind of one skilled in the art having the benefit ofthe teachings presented in the foregoing descriptions and the associateddrawings.

[0115] Another aspect of the invention relates to an aircraft system 300comprising an in-flight entertainment system and at least one camera,such as passenger cameras 302, for providing aircraft surveillance, asbest illustrated in FIGS. 18-19. The illustrated aircraft system 300comprises an entertainment source 304, at least one passenger display(PDU) 306 for displaying images from the entertainment source, and asignal distribution network 310 connecting the entertainment source tothe passenger displays.

[0116] Electronic equipment, carried by an equipment rack 320,interfaces between the entertainment source 304 and the signaldistribution network 310. The illustrated equipment rack 320 includes anaudio/video modulator (AVM) 321, at least one multi-channelreceiver/modulator (MRM) 323 and an RF distribution assembly (RDA) 325.Instead of the electronic equipment being collocated in an equipmentrack 320, the equipment may installed in different spaced apartlocations throughout the aircraft 31 in other embodiments.

[0117] The AVM 321 receives inputs from the passenger cameras 302, aswell as from the entertainment source 304 which may provide pre-recordedinformation, for example. If the entertainment source 304 is a satellitetelevision receiver, such as a DBS receiver, for example, then thesignals are provided to the MRM 323. There may be more than one MRM 323,such as four, for example. The RDA 325 combines the MRM RF outputs tocreate a single RF signal comprising up to 48 audio/video channels, forexample. The RDA 325 amplifies and distributes the composite RF signalto a predetermined number of zone cable outputs via the signaldistribution network 310. The signal distribution network 310 mayinclude a dedicated set of cables interfacing with the various displays306 and 308, or the cables may also support other functions associatedwith the in-flight entertainment system. In other embodiments, thesignal distribution network 310 may be implemented as a wirelessnetwork, or as a combined cable and wireless network.

[0118] The aircraft system 300 further includes at least one pilotdisplay (PDU) 308 in the cockpit area 314 of the aircraft 31 fordisplaying images from the passenger cameras 302. The signaldistribution network 310 connects the passenger cameras 302 to the pilotdisplay 308 via a seat electronic box (SEB) 360. As discussed above, thesignal distribution network 310 includes a cable network as well asdistribution devices, such as the SEBs 360. Since the signaldistribution network 310 is typically routed throughout the aircraft 31for connecting the entertainment source 304 with the passenger displays306, connection of the passenger cameras 302 and the pilot display 308may also be provided via the same signal distribution network. Thisadvantageously eliminates hardware redundancy and helps to reduceequipment and installation costs, particularly for retrofits andupgrades.

[0119] The aircraft system 300 advantageously allows the pilot to viewthe images from the passenger cameras 302 while flying the aircraft. Inthe illustrated embodiment (FIG. 19), four passenger cameras 302 arespaced throughout the passenger area 312 of the aircraft 31. The actualnumber of passenger cameras 302 is based upon the size and layout of theaircraft, and the desired areas to be monitored. The images from thepassenger cameras 302 are displayed on the pilot display 308, and arenot typically displayed on the passenger displays 306. That is, thepassengers do not view the images from the passenger cameras 302.

[0120] Camera control is provided to the pilot via a pilot control unit316 connected to the pilot display 308 via the SEB 360. Depending on thesize of the aircraft 31, there may be two pilot displays 308 in thecockpit area 314, with each display being controlled by a respectivepilot control unit 316. For example, one pilot display 308/pilot controlunit 316 may be on the left side of the cockpit area 314, and anothermay be on the right side.

[0121] Each pilot control unit 316 may have a camera select mode 350 forselecting a desired passenger camera 302 for viewing. Each pilot controlunit 316 may further or alternatively include a scan mode 352 forscanning the images from each passenger camera 302. In other words, theimages from a single passenger camera 302 are momentarily displayedbefore displaying the images from a different passenger camera. Thiscycle continues through each of the remaining passenger cameras 302, andthen repeats. In addition, the pilot display 308 may be configured sothat the images from more than one passenger camera 302 may be displayedat one time, i.e., a split screen, as readily understood by one skilledin the art. The pilot may also have the option to view the images froman external camera 324 and a cargo camera 325. These particular cameraswill be discussed below.

[0122] The pilot may not be limited to viewing images from the variouscameras on the pilot display 308. For instance, the pilot may have theoption of selecting the weather channel via the pilot control unit 316so that weather related information may be displayed on the pilotdisplay 308, for example. A weather related programming channel will bediscussed in greater detail below.

[0123] Another advantageous feature of the aircraft system 300 is basedupon the addition of at least one pilot camera 322 in the cockpit area314 of the aircraft 31 for providing pilot images to the passengerdisplays 306 via the AVM 321 and the signal distribution network 310.This advantageously allows the pilot to selectively address thepassengers, particularly prior to takeoff and landing, for example.

[0124] As discussed above, an external camera 324 may also be positionedfor providing images from outside the aircraft 31. Images from outsidethe aircraft 31 may be of flight critical components, such as the tailsection 328, for example. Other external cameras 324 may also be placedfor providing images of the entry points of the aircraft 31 used by thevarious aircraft support personnel. A cargo camera 325 may be placed inthe cargo bay 315 of the aircraft 31, for example.

[0125] The aircraft system 300 further illustratively includes arecording device 330 for recording the images from the various cameras302, 322, 324 and 325. In addition, the aircraft system 300 furtherillustratively includes a transmitter 332 for transmitting the imagesfrom the various cameras 302, 322, 324 and 325 to a location externalthe aircraft 31 for remote viewing. The illustrated transmitter 332 hasan antenna 333 connected thereto Interface from the AVM 321 may beprovided via an Ethernet connection for providing video snapshots fromthe different cameras to the transmitter 332, as readily appreciated byone skilled in the art. The remote viewing may be while the aircraft 31is in flight or on the ground, and is performed at the schematicallyillustrated monitoring station 370, for example.

[0126] In another embodiment of the aircraft system 300′, theentertainment source is a satellite receiver 305 providing only audiochannels to the passengers, as illustrated in FIG. 20. The satellitereceiver 305 may be compatible with a Sirius Satellite Radio satellite,an XM Satellite Radio satellite, or a WorldSpace satellite, for example,as readily appreciated by those skilled in the art. Since video imagesare not being displayed to the passengers, passenger control units (PCU)71 provide the audio channels received by the satellite receiver 305 tothe passengers via passenger headphones 70 while the pilot continues toreceive images from the various cameras 302′, 324′ and 325′.

[0127] As stated above, the signal distribution network may beimplemented as a cable network 310′, as a wireless network 310″, or as acombined cable and wireless network 310″. Similarly, the interfacebetween the satellite receiver 305 and the equipment rack 320′ may be awired 313 or a wireless 313′ interface, or a combination of both.Likewise, the interface between the various cameras 302′, 324′ and 325′and the equipment rack may be a wired 315 or a wireless 315′ interface,or a combination of both

[0128] Turning now additionally to FIGS. 21 and 22, another feature ofthe present invention is directed to an in-flight entertainment system30 receiving terrestrial signals from a plurality of terrestrialtransmitters 404, 406. For purposes of discussion, the terrestrialtransmitters 404, 406 transmit television (TV) programming channels.However, this aspect of the present invention is not limited to TVprogramming channels, and is compatible with other types of terrestrialtransmitters, such as those associated with voice and data (includinge-mail) communications The partially illustrated in-flight entertainmentsystem 30 further includes an adaptive antenna 400 and a terrestrialreceiver 402, such as a terrestrial TV receiver, for receiving the TVprogramming channels. An antenna 405 is illustratively connected to theterrestrial receiver 402, and at least one display 68 is connected tothe terrestrial receiver 402 via the signal distribution network 41.

[0129] The illustrated signal distribution network 41 is a cablenetwork. In other embodiments, the signal distribution network may beimplemented as a wireless network, or as a combined cable and wirelessnetwork. In addition, if the terrestrial receiver 402 is intended tosupport voice communications, then the VDU 68 may be supplemented orreplaced by a PCU 71. The PCU 71 provides audio channels to a passengervia passenger headphone 70, whereas the VDU 68 provides data (i.e., textand e-mail messages) to the passenger.

[0130] A controller 408 is connected to the adaptive antenna 400 fordetermining a desired terrestrial TV transmitter, and for directing theadaptive antenna 400 for the desired terrestrial TV transmitter. If anew desired terrestrial TV transmitter is determined, then thecontroller 408 redirects the adaptive antenna for the new desiredterrestrial TV transmitter.

[0131] Once the aircraft 32 reaches its flying altitude, the adaptiveantenna 400 typically has a line of sight path to more than oneterrestrial TV transmitter, such as transmitters 404 and 406, forexample. Each transmitter 404 and 406 transmits within the same assignedfrequency allocation, but the transmitted TV programming channels arenot the same. Consequently, this results in the terrestrial TV receiver402 receiving a corrupted signal that is difficult to process. Thecontroller 408 advantageously determines the desired terrestrial TVtransmitter, and directs the adaptive antenna 400 for this transmitter.

[0132] As the aircraft 31 travels, it may become out-of-range of thedesired terrestrial TV transmitter, and become in-range to a new desiredterrestrial TV transmitter. The controller 408 also advantageouslydetermines when to redirect the adaptive antenna 400 for the new desiredterrestrial TV transmitter. In one approach for controlling the adaptiveantenna 400, the controller 408 determines the desired terrestrial TVtransmitter by discriminating among received terrestrial TV signals.

[0133] The illustrated controller 408 includes a signal processor 410for performing the discriminating based upon at least one of a frequencydomain analysis and a time domain analysis of the received terrestrialTV signals, as readily understood by one skilled in the art. The signalprocessor 410 includes an algorithm for weighting the receivedterrestrial TV signals in the time domain as well as in the frequencydomain, with both the amplitude and phase of the signals being weighted.This advantageously allows digital beam steering to be performed inwhich the received terrestrial TV signals are first digitized andweighted using digital signal processing.

[0134] In another approach for controlling the adaptive antenna 400, thecontroller 408 uses knowledge of the position of the terrestrial TVtransmitters 404, 406. That is, the controller 408 operates in a closedloop configuration. Position of the terrestrial TV transmitters, such astransmitter 404 and 406, for example, are stored in a memory 412 withinthe controller 408. The memory 412 is connected to the signal processor410. Alternatively, position of the terrestrial TV transmitters 404, 406may be stored directly in an embedded memory within the signal processor410.

[0135] To determine position of the aircraft 31, the controller 408includes a position determining system 414 connected to the signalprocessor 410. The illustrated position determining system 414 is a GPSreceiver, which has an antenna 415 connected thereto. In lieu of using aposition determining system 414 within the controller 408, the aircraftnavigation system 153 may be used. If the position of the terrestrial TVtransmitters 404, 406 are not known, then the controller 408 operates inan open loop configuration and relies on discrimination among thereceived terrestrial TV signals.

[0136] The adaptive antenna 400 will now be discussed in greater detail.In one embodiment, the adaptive antenna 400 comprises a phased arrayantenna 401 connected to an adaptive processor 411. The adaptiveprocessor 411 interfaces between the signal processor 410 and the phasedarray antenna 401. The adaptive processor 411 steers an antenna beamfrom the phased array antenna 401 towards the desired terrestrial TVtransmitter, such as transmitter 404, for example, based upon commandsfrom the signal processor 410, as readily appreciate by one skilled inthe art. A null from the phased array antenna 400 would then be directedtowards the undesired TV transmitter 406. In an alternative embodiment,the function of the adaptive processor 411 and the function of thesignal processor 410 are combined into a single processor, which may bewithin the controller 408 or external the controller, as readilyappreciated by one skilled in the art.

[0137] The phased array antenna 401 may include several fixed patterns,wherein the adaptive processor 411 selects the desired fixed patternbased upon commands from the signal processor 410, as also readilyappreciate by one skilled in the art. Alternatively, the phased arrayantenna 401 may be a fully adaptive phased array, wherein the adaptiveprocessor 411 selects from an infinite variety of antenna patterns.

[0138] As the aircraft 31 travels along its route, the signal processor410 continues to monitor the received TV programming channels based uponthe different relative phases and amplitudes of the received terrestrialTV signals for determining if a different terrestrial TV transmitter isdesired. In one embodiment the monitored signals are not passed to theterrestrial TV receiver 402. That is, the monitoring is performed in thecontroller 408. In particular, if the signal processor 410 determines anew desired terrestrial TV transmitter, then the signal processorredirects the adaptive antenna via the adaptive processor 411 towardsthe new desired terrestrial TV transmitter, such as transmitter 406, forexample. Alternatively, the signal processing function of the controller408 may be incorporated within the terrestrial TV receiver 402, asreadily appreciated by one skilled in the art.

[0139] Another feature of the phased array antenna 400 is that multiplebeams may be steered or directed so that there is uninterruptedperformance when transitioning from the desired terrestrial TVtransmitter 404 to the new desired terrestrial TV transmitter 406. Inlieu of multiple antenna beams, a time delay may be used to minimize anyinterruption in the transition from one terrestrial TV transmitter toanother.

[0140] In another embodiment, the adaptive antenna 400 comprises aplurality of antennas 403 spaced apart on the aircraft 31. Asillustrated in FIG. 22, the plurality of antennas 403 include fourantennas, for example, with each antenna providing an antenna beam in arespective 90 degree quadrant so that collectively the four antennasprovide a 360 degree coverage. The actual number of antennas may varybased upon the desired level of performance, as readily appreciated byone skilled in the art.

[0141] In this particular embodiment, the controller 408 selects via theadaptive processor 411 the antenna beam from the quadrant that includesthe desired terrestrial TV transmitter 404. To provide a null toward theundesired terrestrial TV transmitters, reception from the remainingantennas are not passed to the terrestrial TV receiver 402. However, thesignal processor 410 continues to periodically monitor the receivedterrestrial TV signals from these antennas for determining if a newdesired terrestrial TV transmitter 406 should be selected. If the signalprocessor 410 determines a new desired terrestrial TV transmitter 406,then the signal processor selects via the adaptive processor 411 adifferent antenna 403 having its antenna beam covering the quadrant thatincludes the new desired terrestrial TV transmitter 406.

[0142] Referring now to FIG. 23, the weather information feature of thein-flight entertainment system 30 will now be discussed. The in-flightentertainment system 30, only select components of which are illustratedin FIG. 23, comprises at least one entertainment source 304, a satelliteweather information receiver 500 for receiving at least one weatherrelated programming channel from at least one satellite, and a pluralityof displays 68 for displaying images from the at least one entertainmentsource and for displaying weather related information corresponding toselected geographic areas. A signal distribution network 310 connectsthe entertainment source 304 and the satellite weather informationreceiver 500 to the plurality of displays 68.

[0143] The in-flight entertainment system 30 further comprises a mapimage device 512 connected to the satellite weather information receiver500 and to the plurality of displays 68 for storing map images of theselected geographic areas. The displayed weather related informationincludes the map images. The map image device 512 also comprises amoving map image generator for generating a moving representation of theaircraft position on the map images.

[0144] At least one processor 506 is connected to the satellite weatherinformation receiver 500 for determining the weather related informationcorresponding to the selected geographic areas. The processor 506compares the information identifying the selected geographic withinformation provided by the at least one weather related programmingchannel. In other words, only a subset of the received weather relatedinformation is selected to be displayed. Since the received weatherrelated programming channel is a digital signal, the processor 506compares stored information identifying the selected geographic areas tothe received weather related programming channel, as readily understoodby one skilled in the art.

[0145] The selected geographic areas comprise geographic areas along aflight path of the aircraft, for example. As the aircraft travels alongits flight path, the displays 68 scroll through the weather relatedinformation for each selected geographic area. The selected geographicareas also include a destination of the aircraft. This aspect of theweather information feature of the in-flight entertainment system 30does not require any input from the passengers. The selected geographicareas, which are input into the processor 506 before flight or duringthe flight, are selected based upon the flight path of the aircraft.This entry may be accomplished by the pilot through a pilot controlunit, for example.

[0146] Another aspect of the weather information feature is that thepassengers may input information into the system for obtaining weatherrelated information on a particular geographic area. A plurality ofcontrol units 71 are connected to the plurality of displays 68 forselecting the geographic areas. Each control unit 71 is associated witha respective display, and comprises input means or an input device forselecting the geographic areas. The geographic areas are selected byentering at least one of a city name, a zip code and an area code viathe input device. The input device may be an alpha-numeric keypad, forexample.

[0147] The selected geographic area may be a final destination of anaircraft passenger, and consequently, any passenger is able to obtaincurrent weather related information for this particular area via theinput device 504. The weather related information 508 displayed on thepassenger displays 68 includes the high and low temperatures, relativehumidity, and the projected weather forecast, for example.

[0148] For example, if Orlando, Fla. is the final destination of thepassenger, the passenger enters “Orlando, Fla.” via the input device504. A zip code, area code or other pertinent information may be enteredfor identifying the selected geographic area. Once “Orlando, Fla.” hasbeen entered, this term is compared with the information provided by theweather related programming channel for a match. Since the weatherrelated programming channel is a digital signal, the PCU 71 converts“Orlando, Fla.” into a digital signal so that a digital comparison canbe made.

[0149] If the passenger does not select a geographic area, a defaultposition for the selected geographic area may correspond to a currentposition of the aircraft 31, for example. The current position of theaircraft 31 may be provided by a positioning determining system, such asa GPS receiver.

[0150] The in-flight entertainment system further includes a pluralityof signal distribution devices 45 connecting the satellite weatherinformation receiver 500 to the passenger displays 68. The at least oneprocessor 506 may comprise a plurality of processors, with eachprocessor being included within a respective signal distribution device45.

[0151] In one embodiment, the satellite weather information receiver 500operates within a frequency range of about 1 to 3 GHz, for example. Thesatellite providing the weather related programming channel may thus bea Sirius Satellite Radio satellite, an XM Satellite Radio satellite, ora WorldSpace satellite, as readily appreciated by those skilled in theart. However, operation of the weather information feature as disclosedherein is not limited to this particular frequency range and totransmissions from these satellites.

[0152] Another embodiment 30′ of the weather information feature of thein-flight entertainment system will now be discussed with reference toFIG. 24. In this particular embodiment, a satellite receiver 500′ isused for receiving at least one weather related programming channel andat least one entertainment related programming channel. The weatherrelated programming channel is for the pilot's benefit for receivingaccurate weather information that is regularly updated while in flight.

[0153] The weather related information may be displayed on a pilotdisplay 308. A pilot control unit 77 is connected to the pilot display308 for selecting the geographic areas, and includes an input device forselecting these areas, as discussed above for the passenger controlunits 71. The pilot display 308 and the pilot control unit 77 may beimplemented as separate units or as a single integrated device.

[0154] In lieu of a pilot display 308, the weather related informationmay be displayed on an on-board computer 309, which may be mountedwithin the cockpit or may be a portable laptop computer carried by thepilot. The geographic areas would also be selected by the on-boardcomputer 309. When the aircraft is on the ground, weather informationmay be provided to the pilot via a wireless data link 57.

[0155] If the entertainment related information provided to thepassengers by the satellite receiver 500′ is audio only, then passengercontrol units (PCU) 71 may be used for providing this audio to thepassengers via passenger headphones 70. However, in other embodiments,the weather information may also be provided to the passengers (via thepassenger displays 68) as discussed above, along with the weatherinformation being provided to the pilot.

[0156] Referring now additionally to the flowchart of FIG. 25 and theassociated schematic block diagram of FIG. 26, another advantageousfeature of the invention relates to determination of a respectivepricing level on the available features of the in-flight entertainmentsystem 30 for each passenger. From the start (Block 600), information iscollected on passengers of the aircraft at Block 602. The informationmay be generated based upon frequent flyer profiles and an airlinepassenger database, for example. The collected information may be storedin a memory 621 connected to a processor 620 within the SEB 45.

[0157] The in-flight entertainment system 30 uses the collectedinformation at Block 604 for determining a respective pricing level foreach passenger on the available features of the system. Theentertainment source 614 provides at least one programming channel, andthe available features includes the at least one programming channel.The entertainment source 614 comprises a satellite TV receiver, such asa direct broadcast (DBS) receiver, for example.

[0158] The available features of the in-flight entertainment system 30may also include instant messaging, and may provide connecting gateinformation and other travel related information. The other travelrelated information may include hotel and rental car information, forexample. In addition, the collected information may affect the pricinglevels for the various duty free items offered to each passenger whentraveling overseas.

[0159] The method further includes determining a seating location ofeach passenger based upon an assigned passenger seating list at Block606. A passenger is preferably identified at Block 608 before displayingthe respective pricing level. This ensures that the passenger receivesthe correct pricing level.

[0160] The identifying may also be performed using a token reader 72 anda token 210 associated therewith. In the illustrated embodiment, thetoken reader 72 comprises a card swipe reader, and the token 210comprises a substrate 211 and a magnetic strip 212 thereon. Theprocessor 620 reads the magnetic strip.

[0161] After identification, the respective pricing level 623 isdisplayed on an associated passenger display at Block 610. The tokenreader 72 may comprise a payment token reader, and the token 210comprises a payment token, such as a credit card. Consequently, themethod further includes a passenger using the payment token 210 to pay,if necessary, for selected features of the in-flight entertainmentsystem 30 according to the respective pricing level. The method ends atBlock 612.

[0162] The collected information may be based upon frequent flyerprofiles, a separate airline database, and an assigned passenger seatinglist, for example. The collected information is preferably updatedbefore each flight. Passengers that frequently travel and passengersthat fly first class would have a lower pricing level on the availablefeatures of the in-flight entertainment system 30 as compared topassengers that seldom travel. A respective pricing level would thusvary between passengers in first class and in coach. Premium serviceswould then be provided at little or no cost to a passenger in firstclass, whereas the same services would be offered to a passenger incoach but at a higher cost.

[0163] The illustrated processor 620 generates on the passenger displays68 a respective pricing level on available features of the in-flightentertainment system 30 for each passenger. As noted above, eachrespective pricing level is based upon information collected on aircraftpassengers. The collected information may be stored in the memory 621.The processor 620 also determines a seating location of each passengerbased upon an assigned passenger seating list.

[0164] The illustrated processor 620 is included within a respectiveseat electronics box 45 connecting the entertainment source 614 to thepassenger displays 68. A PCU 71 is illustratively connected to the SEB45, and passenger headphones 70 are connected to the PCU.

[0165] Referring now additionally to the flowchart of FIG. 27 and theassociated schematic block diagram of FIG. 28, another advantageousfeature of the in-flight entertainment system 30 relates to selectivelymatching advertisements based upon passenger profiles. From the start(Block 700), information is collected on passengers of the aircraft atBlock 702, and passenger profiles are generated based upon the collectedinformation.

[0166] The method according to the present invention advantageouslygenerates a profile for each passenger, and selectively matchesadvertisements to each passenger based upon the generated profile. Thisallows the airlines to generate increased advertisement revenue. Thecollected information may be based upon frequent flyer profiles andairline passenger databases, for example.

[0167] Passenger profiles are selectively matched to the passengerprofiles at Block 704. The method further includes determining a seatinglocation of each passenger based upon an assigned passenger seating listat Block 706. In addition, at least one flight parameter of the aircraft31 is monitored at Block 708. The at least one flight parameter maycomprise at least one of a geographic location of the aircraft 31, anestimated time of arrival of the aircraft, and destination of theaircraft.

[0168] A passenger is identified at Block 710 before displaying theselectively matched passenger advertisements on an associated passengerdisplay 68. This ensures that the correct passenger receives theappropriate advertisements. The verifying may be performed using a tokenreader 72 and a token 210 associated therewith. After verification, theselectively matched passenger advertisements corresponding to respectivepassenger profiles are displayed at Block 712 based upon the monitoredflight parameter. The method ends at Block 714.

[0169] For example, as the aircraft 31 approaches its final destination,the flight control computer 700 reports the position of the aircraft 31to a processor 702. In lieu of the flight control computer 700, aposition determining system, such as a GPS receiver, may be used toprovide the position of the aircraft 31 to the processor 702.

[0170] The processor 702 is programmed to generate advertisements withina predetermined range of the airport, such as 100 miles, for example.Other aircraft parameters may be used to trigger display of theadvertisements, as mentioned above. If a passenger profile indicatesthat the passenger is an avid fisherman, and the passenger's destinationis Orlando, for example, then the selectively matched advertisements 704are directed toward deep-sea fishing off the coast of Florida.

[0171] A map image storage device 708 connected to the processor 702provides an image 710 of the coast of Florida. This directly enhancesthe displayed advertisement 704. The advertisement 704 may includeinformation on chartered fishing boats, and even lodging and restaurantinformation. A memory 712 is also connected to the processor 702 forstoring the selectively matched passenger advertisements, and thepassenger profiles. Alternatively, the memory may be embedded within theprocessor 702.

[0172] The in-flight entertainment system 30 also comprises anentertainment source 706, such as a direct broadcast (DBS) receiver. Theentertainment source 706 may also be used to provide the pre-recordedadvertisements. Alternatively, the passenger advertisements from theentertainment source 706 may be inserted with other programming channelsor may appear on its own dedicated channel(s). The illustrated processor702 may be included within a respective SEB 45 connecting the satellitereceiver to the passenger displays 68. A PCU 71 is illustrativelyconnected to the SEB 45, and passenger headphones 70 are connected tothe PCU.

[0173] Many modifications and other embodiments of the invention willcome to the mind of one skilled in the art having the benefit of theteachings presented in the foregoing descriptions and the associateddrawings. Therefore, it is to be understood that the invention is not tobe limited to the specific embodiments disclosed, and that modificationsand embodiments are intended to be included within the scope of theappended claims.

[0174] In addition, other features relating to the aircraft in-flightentertainment system are disclosed in copending patent applicationsfiled concurrently herewith and assigned to the assignee of the presentinvention and are entitled AIRCRAFT IN-FLIGHT ENTERTAINMENT SYSTEMRECEIVING TERRESTRIAL TELEVISION BROADCAST SIGNALS AND ASSOCIATEDMETHODS, attorney docket number 59019; AIRCRAFT IN FLIGHT ENTERTAINMENTSYSTEM PROVIDING WEATHER INFORMATION AND ASSOCIATED METHODS, attorneydocket number 59020; AIRCRAFT IN-FLIGHT ENTERTAINMENT SYSTEM GENERATINGA PRICING STRUCTURE FOR AVAILABLE FEATURES, AND ASSOCIATED METHODS,attorney docket number, 59021; and AIRCRAFT IN-FLIGHT ENTERTAINMENTSYSTEM PROVIDING PASSENGER SPECIFIC ADVERTISEMENTS, AND ASSOCIATEDMETHODS, attorney docket number 59022, the entire disclosures of whichare incorporated herein in their entirety by reference.

That which is claimed is:
 1. An aircraft system comprising: at least oneentertainment source; at least one passenger display for displayingimages from said at least one entertainment source; a signaldistribution network connecting said at least one entertainment sourceto said at least one passenger display; at least one camera forproviding aircraft surveillance; and at least one pilot display fordisplaying images from said at least one camera; said signaldistribution network connecting said at least one camera to said atleast one pilot display.
 2. An aircraft system according to claim 1wherein said at least one camera provides images of inside the aircraft.3. An aircraft system according to claim 1 wherein said at least onecamera comprises a plurality of cameras spaced throughout a cabin areaof the aircraft.
 4. An aircraft system according to claim 1 wherein saidat least one camera provides images of outside the aircraft.
 5. Anaircraft system according to claim 1 further comprising at least onepilot control unit connected to said at least one pilot display.
 6. Anaircraft system according to claim 5 wherein said at least one cameracomprises a plurality of cameras; and wherein said at least one pilotcontrol unit has a camera select mode for selecting the images from adesired camera for viewing.
 7. An aircraft system according to claim 6wherein said at least one pilot control unit further has a scan mode forscanning the images from each camera.
 8. An aircraft system according toclaim 1 wherein said at least one camera comprises: at least onepassenger camera in a cabin area of the aircraft for providing images tosaid at least one pilot display; and at least one pilot camera in acockpit area of the aircraft for providing pilot images to said at leastone passenger display.
 9. An aircraft system according to claim 1further comprising a recording device for recording the images from saidat least one camera.
 10. An aircraft system according to claim 1 furthercomprising a transmitter for transmitting the images to a locationexternal the aircraft for remote viewing.
 11. An aircraft systemaccording to claim 1 wherein said at least one entertainment sourcecomprises a satellite television (TV) receiver.
 12. An aircraft systemaccording to claim 11 wherein said satellite TV receiver comprises adirect broadcast satellite (DBS) receiver.
 13. An aircraft systemaccording to claim 1 wherein said at least one passenger displaycomprises a plurality of seatback displays.
 14. An aircraft systemaccording to claim 1 wherein said signal distribution network comprisesa cable network and signal distribution devices.
 15. An aircraftcomprising: a fuselage comprising a cockpit area and a cabin area; andan aircraft system carried by said fuselage and comprising at least oneentertainment source, at least one passenger display for displayingimages from said at least one entertainment source, a signaldistribution network connecting said at least one entertainment sourceto said at least one passenger display, at least one passenger camera inthe cabin area for providing surveillance, and at least one pilotdisplay in the cockpit area for displaying images from said at least onepassenger camera, said signal distribution network also connecting saidat least one passenger camera to said at least one pilot display.
 16. Anaircraft according to claim 15 further comprising at least one externalcamera connected to said at least one pilot display for providing imagesof outside the aircraft.
 17. An aircraft according to claim 15 whereinsaid at least one passenger camera comprises a plurality of passengercameras spaced throughout the cabin area of the aircraft.
 18. Anaircraft according to claim 15 wherein said aircraft system furthercomprises at least one pilot control unit connected to said at least onepilot display.
 19. An aircraft according to claim 18 wherein said atleast one passenger camera comprises a plurality of passenger cameras;and wherein said at least one pilot control unit has a camera selectmode for selecting the images from a desired passenger camera forviewing.
 20. An aircraft according to claim 19 wherein said at least onepilot control unit further has a scan mode for scanning the images fromeach passenger camera.
 21. An aircraft according to claim 15 furthercomprising at least one pilot camera in the cockpit area for providingpilot images to said at least one passenger display.
 22. An aircraftaccording to claim 15 wherein said aircraft system further comprises arecording device for recording the images from said at least onepassenger camera.
 23. An aircraft according to claim 15 wherein saidaircraft system further comprises a transmitter for transmitting theimages to a location external the aircraft for remote viewing.
 24. Anaircraft according to claim 15 wherein said at least one entertainmentsource comprises a satellite television (TV) receiver.
 25. An aircraftaccording to claim 24 wherein said satellite TV receiver comprises adirect broadcast satellite (DBS) receiver.
 26. An aircraft according toclaim 15 wherein said at least one passenger display comprises aplurality of seatback displays.
 27. An aircraft system according toclaim 15 wherein said signal distribution network comprises a cablenetwork and signal distribution devices.
 28. An aircraft systemcomprising: at least one entertainment source; at least one passengercontrol unit; a signal distribution network connecting said at least oneentertainment source to said at least one passenger control unit; atleast one camera for providing aircraft surveillance; and at least onepilot display for displaying images from said at least one camera; saidsignal distribution network connecting said at least one camera to saidat least one pilot display.
 29. An aircraft system according to claim 28wherein said signal distribution network comprises at least one of acable network, a wireless network, and a combined cable and wirelessnetwork.
 30. An aircraft system according to claim wherein said at leastone passenger control unit comprises a headphone connection forinterfacing with a passenger headphone.
 31. An aircraft system accordingto claim 28 wherein said at least one passenger control unit comprises aselector for selecting a desired audio channel.
 32. An aircraft systemaccording to claim 28 wherein said at least one camera provides imagesof inside the aircraft.
 33. An aircraft system according to claim 28wherein said at least one camera comprises a plurality of cameras spacedthroughout a cabin area of the aircraft.
 34. An aircraft systemaccording to claim 28 wherein said at least one camera provides imagesof outside the aircraft.
 35. An aircraft system according to claim 28further comprising at least one pilot control unit connected to said atleast one pilot display.
 36. An aircraft system according to claim 35wherein said at least one camera comprises a plurality of cameras; andwherein said at least one pilot control unit has a camera select modefor selecting the images from a desired camera for viewing.
 37. A methodfor operating an aircraft system comprising at least one entertainmentsource, at least one passenger display, a signal distribution networkconnecting the least one entertainment source to the at least onepassenger display, at least one camera for providing aircraftsurveillance, at least one pilot display, and the signal distributionnetwork connecting the at least one camera to the at least one pilotdisplay, the method comprising: displaying images from the at least oneentertainment source on the at least one passenger display; anddisplaying images from the at least one camera on the at least one pilotdisplay.
 38. A method according to claim 37 wherein the at least onecamera provides images of inside the aircraft.
 39. A method according toclaim 37 wherein the at least one camera comprises a plurality ofcameras spaced throughout a cabin area of the aircraft.
 40. A methodaccording to claim 37 wherein the at least one camera provides images ofoutside the aircraft.
 41. A method according to claim 37 wherein theaircraft system further comprises at least one pilot control unitconnected to the at least one pilot display.
 42. A method according toclaim 41 wherein the at least one camera comprises a plurality ofcameras; and wherein the at least one pilot control unit has a cameraselect mode for selecting the images from a desired camera for viewing.43. A method according to claim 42 wherein the at least one pilotcontrol unit further has a scan mode for scanning the images from eachcamera.
 44. A method according to claim 37 wherein the at least onecamera comprises at least one passenger camera in a cabin area of theaircraft, and at least one pilot camera in a cockpit area of theaircraft; and wherein displaying the images from the at least one cameracomprises: displaying images from the at least one passenger camera onthe at least one pilot display; and displaying images from the at leastone pilot camera on the at least one passenger display.
 45. A methodaccording to claim 37 further comprising recording the images from theat least one camera.
 46. A method according to claim 37 furthercomprising transmitting the images to a location external the aircraftfor remote viewing.
 47. A method according to claim 37 wherein the atleast one entertainment source comprises a satellite television (TV)receiver.
 48. A method according to claim 47 wherein the satellite TVreceiver comprises a direct broadcast satellite (DBS) receiver.
 49. Amethod according to claim 37 wherein the at least one passenger displaycomprises a plurality of seatback displays.